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FR3106614B1 - Turbomachinery part or set of parts - Google Patents

Turbomachinery part or set of parts Download PDF

Info

Publication number
FR3106614B1
FR3106614B1 FR2000668A FR2000668A FR3106614B1 FR 3106614 B1 FR3106614 B1 FR 3106614B1 FR 2000668 A FR2000668 A FR 2000668A FR 2000668 A FR2000668 A FR 2000668A FR 3106614 B1 FR3106614 B1 FR 3106614B1
Authority
FR
France
Prior art keywords
parts
fin
blade
platform
turbomachinery
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2000668A
Other languages
French (fr)
Other versions
FR3106614A1 (en
Inventor
William Henri Joseph Riera
Gabriel Jacques Victor Mondin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran SA
Original Assignee
Safran SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran SA filed Critical Safran SA
Priority to FR2000668A priority Critical patent/FR3106614B1/en
Priority to CN202180016546.4A priority patent/CN115176070B/en
Priority to PCT/FR2021/050093 priority patent/WO2021148751A1/en
Priority to US17/794,077 priority patent/US11982204B2/en
Priority to EP21705587.0A priority patent/EP4093945B1/en
Publication of FR3106614A1 publication Critical patent/FR3106614A1/en
Application granted granted Critical
Publication of FR3106614B1 publication Critical patent/FR3106614B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/73—Shape asymmetric
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Pièce ou ensemble de pièces d’une turbomachine comprenant au moins des première et deuxième pales, et une plateforme à partir de laquelle s'étendent les pales. La plateforme présente entre l'intrados de la première pale et l'extrados de la deuxième pale une surface non axisymétrique définissant au moins une ailette. La pièce est caractérisée en ce qu’une section transversale de l’ailette est asymétrique. Figure pour l’abrégé : Fig. 3Part or set of parts of a turbomachine comprising at least first and second blades, and a platform from which the blades extend. The platform has between the lower surface of the first blade and the upper surface of the second blade a non-axisymmetric surface defining at least one fin. The part is characterized in that a cross section of the fin is asymmetrical. Figure for the abstract: Fig. 3

FR2000668A 2020-01-23 2020-01-23 Turbomachinery part or set of parts Active FR3106614B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2000668A FR3106614B1 (en) 2020-01-23 2020-01-23 Turbomachinery part or set of parts
CN202180016546.4A CN115176070B (en) 2020-01-23 2021-01-19 Turbine component or assembly of components
PCT/FR2021/050093 WO2021148751A1 (en) 2020-01-23 2021-01-19 Turbomachine part or assembly of parts
US17/794,077 US11982204B2 (en) 2020-01-23 2021-01-19 Turbomachine part or assembly of parts
EP21705587.0A EP4093945B1 (en) 2020-01-23 2021-01-19 Turbomachine part or assembly of parts

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000668A FR3106614B1 (en) 2020-01-23 2020-01-23 Turbomachinery part or set of parts
FR2000668 2020-01-23

Publications (2)

Publication Number Publication Date
FR3106614A1 FR3106614A1 (en) 2021-07-30
FR3106614B1 true FR3106614B1 (en) 2021-12-24

Family

ID=70295352

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2000668A Active FR3106614B1 (en) 2020-01-23 2020-01-23 Turbomachinery part or set of parts

Country Status (5)

Country Link
US (1) US11982204B2 (en)
EP (1) EP4093945B1 (en)
CN (1) CN115176070B (en)
FR (1) FR3106614B1 (en)
WO (1) WO2021148751A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024209167A1 (en) 2023-04-07 2024-10-10 Safran Stator member for a turbine engine, equipped with at least one fin, and method for mounting at least one fin in the stator member

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3134416A1 (en) * 2022-04-11 2023-10-13 Safran Finned stator part in a turbomachine
FR3139595B1 (en) 2022-09-09 2024-12-13 Safran Guide vane intended to be fixed on a stator ferrule of a gas turbine engine
FR3147835A1 (en) 2023-04-11 2024-10-18 Safran Improved Variable Timing Stator and Method Using Such a Stator

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2907519B1 (en) * 2006-10-20 2011-12-16 Snecma FLOOR PLATFORM FLOOR
DE102008060424A1 (en) * 2008-12-04 2010-06-10 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with sidewall boundary layer barrier
JP5842382B2 (en) * 2011-05-13 2016-01-13 株式会社Ihi Gas turbine engine
JP5964263B2 (en) * 2013-02-28 2016-08-03 三菱日立パワーシステムズ株式会社 Rotor cascade of axial flow turbine and axial flow turbine
FR3014943B1 (en) * 2013-12-18 2019-03-29 Safran Aircraft Engines TURBOMACHINE PIECE WITH NON-AXISYMETRIC SURFACE
US10240462B2 (en) * 2016-01-29 2019-03-26 General Electric Company End wall contour for an axial flow turbine stage

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024209167A1 (en) 2023-04-07 2024-10-10 Safran Stator member for a turbine engine, equipped with at least one fin, and method for mounting at least one fin in the stator member
FR3147586A1 (en) 2023-04-07 2024-10-11 Safran STATOR COMPONENT FOR A TURBOMACHINE EQUIPPED WITH AT LEAST ONE FIN AND METHOD FOR MOUNTING AT LEAST ONE FIN IN THE STATOR COMPONENT.

Also Published As

Publication number Publication date
FR3106614A1 (en) 2021-07-30
US20230138043A1 (en) 2023-05-04
WO2021148751A1 (en) 2021-07-29
CN115176070A (en) 2022-10-11
US11982204B2 (en) 2024-05-14
CN115176070B (en) 2024-11-05
EP4093945B1 (en) 2024-08-21
EP4093945A1 (en) 2022-11-30

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